Gyrostabilized bomb control system



Aug. 20, 1946. J.\ H. HAMMOND, JR 2,406,293

GYROSTABILIZED BOMB CONTROL SYSTEM Filed March 16,1943 5 Sheets-Sheet 1 INVENTOR JOHN HAYS HAMMOND,-JR.

Aug. l?

, 1945- J. H. HAMMOND, JR 2,406,293

GYROSTABILIZED BOMB CONTROL SYSTEM Filed March 16, 1943 5 Sheets-Sheet 2 TRANSMITTER RADIO RECEIVER 95 99 EXPLOSIVE INVENTOR 8 JOHN HAYS HAMMOND,JR.

Aug. 20, 1946. H MM ND, R 2,406,293

GYROSTABILIZED BOMB CONTROL SYSTEM Filed March '16, 1943 5 Sheets-Sheet 5 G) 1: Id 4 u] O U u:

NI N NTOR RNEY INVE JOHN HAYS HAMMOND,JR.

20, 1946- J. H. HAMMOND, JR 2,406,293

GYROSTABILIZED BOMB CONTROL SYSTEM Filed March 16, 1943 5 Sheets-Sheet 4 INVENTOR JOHN HAYS HAMMOND,JR.

Patented Aug. 20, 1946 s'r'rss UNIT I;

Z,it6,23

ATEN'E' FiQ Claims.

The invention relates to the radio-dynamic control of aerial bombs and more particularly to a radio control system which can selectively steer the falling bomb in any one of a plurality of directions.

The invention provides means for controlling the direction of descent of a bomb in connection with a gyroscope or other stabilizing means in which the bomb may be steered in any one of a plurality of directions in azimuth irrespective of the horizontal rotation of the bomb.

The invention also consists in certain new and original features of construction and combinations of parts hereinafter set forth and claimed.

Although the novel features which are believed to be characteritic of this invention will be particularly pointed out in the claims appended hereto, the invention itself, as to its objects and advantages, the mode of its operation and the manner of its organization may be better understood by referring to the following description taken in connection with the accompanyin drawings forming a part thereof, in which Figure 1 is a diagrammatic illustration of a portion of a plane, including the bomb bay;

Figure 1a is a perspective view of a bomb as released from the plane of Figure 1;

Figure 2 is a block diagram of the transmitting circuits on the plane;

Figure 3 illustrates diagrammatically the receiving circuits located in the bomb;

Figure 4 is a partial section thru a bomb illustrating diagrammatically the control apparatus for steering the bomb;

Figure 5 is a section taken on line 55 of Fig.4;

Figure 6 is a section taken on line 6-5 of Fig.4;

Fig. '7 is a partial section thru the bomb illustrating diagrammatically the control apparatus in the position it will assume during the descent of the bomb;

Figs. 8 and 9 are end views of the bomb; and

Fig. 10 is a plan View of the distributing systern.

Like reference characters denote like parts in the several figures of the drawings.

In the following description parts will be identified by specific names for convenience, but they are intended to be as generic in their application to similar parts as the art will permit.

Referring to the accompanying drawings and more particularly to Figure l the plane II is shown as provided with the usual bomb bay l2 behind which is an opening iii in which is 10- cated the antenna system M of the transmitter to be described. This antenna system is mounted on suitable means, shown as gimbal rings l5, so that it may be pointed in any desired direction. A sighting means, shown as a telescope I6, is attached to the antenna system It to facilitate following the bomb in its descent. The antenna system !4 is of the type adapted to radiate polarized, directional, short waves in the form of a beam. In the embodiment shown this system comprises a dipole radiator I la mounted in a reflector system 64?). 'It is to be understood, however, that any standard type of directional polarized beam short wave radiator may be used.

The bomb ll is provided with the usual fins H8 in which are located two sets of rudders l9 and 2i whose axes of rotation are at right angles to each other. Mounted on the ends of the fins l8 are two directional receiving antennas 22 and 23 the axes of which are located in planes at right angles to each other, and preferably in the planes of the axes of the rudder t9 and M. The antennas 22 and 23 are shown as similar in construction to the antenna l4 and are of the type suited to receive polarized short waves from a given direction only. The antennae are shown as comprising wave receiving members 22a and 23a and directional members 2212 and 23b which correspond to the reflector Mb. The directional members are suited to make the receiving ele ments receptive to signals received from above and to shield the receiving members from waves propagated from the ground and from horizontal waves, so that possibility of interference with the control beam transmitted from the plane is eliminated.

Fig. 2 is a diagrammatic illustration of the transmitter l58 which may be similar in design to the transmitter depicted in Fig. 2 of my copending application, Serial Number 458.938. The transmitter is of a type to generate a short Wave carrier modulated by a control frequency. Four keys 38-33 are connected to vary the control frequency when individually depressed to produce the A, B, C and D control frequencies respectively. The transmitter I53 is connected to the antenna M by means of the transmission line I33.

Fig. 3 is a diagrammatic illustration of the receiver l59 which may be similar in design to the receiver depicted in Fig. 3 of my co-pending application 458,938 and is connected to the directive antenna system 22-23. The receiver l59 feeds power tubes -68 which are energized by batteries at mil-498. The power tubes 65-48 are connected to four solenoids II-4A thru a distributing system I69. The distributing system I90 includes four brushes i5 II64 which are connected by conductors Il98 to the plates of the power tubes 6S. The brushes Isl-464 engage four slip rings I'I iIM which are mounted on a circular block of insulation I'll! to be more fully described hereinafter. Secured to the block of insulation I79 are four brushes I15, I15, l1! and H8 which are electrically connected to the four slip rings III, I14, I12 and I13 respectively. The four brushes Il5-Il8 engage four quadrant segments I8| to I84 which in turn are connected by conductors II88 to one side of the windings of the solenoids T4, t2 and *13' respectively, the other sides of the windings being connected by a conductor I89 to the battery I68.

In Figure 4 is shown the apparatus for controlling the rudders I9 and 21 in response to the energization of the four solenoids 'II'I4 illuse trated in Figure 3. The two sets of rudders I9 and 2| are connected by links 8| to piston rods 92 which are attached to pistons 83 which reciprocate in two cylinders 84 and 85. Balanced compression springs 86 are provided for normally holding the pistons 83 and therefore the rudders l9 and 2I in a central position,

The pistons 83 are actuated by air under pressure which is supplied from a tank 81. This tank is shown as being connected by a pipe 88 to a a funnel shaped opening in the nose of the bomb Ii. A flask containing air under pressure could also be used as a source of compressed air if desired. The tank 81 is connected to the cylinders 3:1 and 85 by means of conduits 9I and the supply of air to the interior of the cylinders 89 and 35 is controlled by two piston valves 92 and 99 respectively. The valve 92 is operated in opposite directions by means of the solenoids II and 'I2 and the valve 93 is operated in opposite directions by means of the solenoids I3 and M. Balanced compression springs 99 are provided to maintain the valves 92 and 99 in a central position when the solenoids I lld are de-energized.

Two transverse bulkheads 95 and 96 are provided which divide the bomb into three compartments 91, 98 and 99. The compartment 9? contains the control apparatus just described and the radio receiver I59 which is mounted on the bulkhead 96. The compartment 96 contains the gyroscopic apparatus presently to be described and the compartment 99 is filled with a high explosive, such for example as TNT and is provided with the usual fuses, not shown, for detonating the explosive charge when the bomb reaches its target.

In the compartment 98 are mounted two cross members ISI and I92 to which is pivoted a gimbal ring I93. In the gimbal ring I93 is pivoted a gyroscope I94 to the lower part of which is attached a Weight I95. Mounted on the gimbal ring I93 is the circular block of insulation IIIJ, already described in connection with Fig, 3, which carries the four slip rings I'II-IIll which in turn are engaged by the four brushes I5 II 6d. These brushes are mounted on a block of insulation I96 which is secured to the cross member I92. The four quadrantsegments I8 II84 are mounted on brackets fill-94 of insulating material which are secured to'the casing of the bomb It.

In Fig. 4 the bomb H is shown as suspended from the bomb rack 295. scope I96 up to speed before the bomb is released a source of A. C. current 298 is provided and is connected thru a switch 29? to a double contact For bringing the gyro-,

plug 268 mounted on the bomb rack 265. The contacts of the plug 208 engage the contacts of a receptacle 299 mounted on the bomb I'I. Pivotally mounted in the cross member I9! is an arm ZI I the outer end of which engages the top of the gyroscope I94. A spring 2H1 tends to rotate the arm 2 in a counter clockwise direction. The contacts of the receptacle 299 are connected by flexible conductors Hz to contacts 2I3 which engage the winding 264 of the gyroscope I95.

Mounted on the end of the arm MI is a fiat spring 2I5 the end of which is turned up. Pivotally mounted on the casing of the bomb It is a member 2136. A spring 2 I1 is provided which tends to'rotat the member 2 It in a counter clockwise direction. Mounted on the bomb rack 295 is a cylinder ZIB in which reciprocates a piston 259 to which is attached a plunger 22! which passes thru an opening in the casing of the bomb I1 and engages the spring 2I5. A compression spring 222 is mounted in the cylinder 2I8 and tends to hold the arm 2 in engagement with the gyroscope I95.

Operation When the bomb is assembled the gyroscope I94 is placed in the position shown in Fig. 4, the arm 2 I I is moved into engagement with the top as the gyroscope and the member 2 I6 is rotated into the position shown in dotted lines so that it engages the end of the spring M5. When the bomb I1 is placed in the bomb rack 295 the plug 298 fits into the receptacle 299 and the plunger 22!. passes thru the hole in the casing of the bomb I1 and engages the spring 2I5 which is moved downward sufiiciently to release the member 2I5 which is rotated in a counter clockwise direction under the action of the spring ZI'I into the position shown in full lines.

As the bomber approaches the target the switch 29'? is closed which closes a circuit from the generator 298 thru the plug 298, receptacle 299, conductors 2I2, contacts 2I3 to the winding of the gyroscope 2 I i. This causes the rotating element of the gyroscope I98 to be brought up to and maintained at speed. The gyroscope I94 is held in the position shown by means of the arm 2II so that during any maneuvers of the bomber the gyroscope I99 will be held fixed in the position shown with respect to th bomb I'I.

When the bomb I1. is released the plug 298 is disengaged from the receptacle 299 and the plunger 22! is disengaged from the pring 2H5. This allows the arm 2 I I to be rotated in a counter clockwise direction under the action of the spring 2H) which leaves the gyroscope I94 free in space. If the bomb It should rotate about its longitudinal axis while in a horizontal position shortly after leaving the bomb rack the gyroscope I94 will remain in a vertical position due to the action of the weight I95 which will cause the gimbal ring I93 to rotate about its pivot points.

As the nose of the bomb drops and it assumes the vertical position of descent the gyroscope I94 which remains fixed in space, will assume the position relative to the bomb I? shown in Fig. '7. In this position the four brushes IIE-IEE will be in the positions shown in Figs. 3 and 5, which when the bomb is descending vertically are plan views looking in the direction of the descent of the bomb.

The four brushes Il5-I'I8 will be maintained in fixed positions in space during the descent of the bomb by the action of the gyroscope I94 and are independent of the rotation of the bomb about its longitudinal axis. The contact IIB will, therefore, always be maintained in the direction in space in which the bomber I I was travelling at the time of th release of the bomb II. The contact I18 will always be pointed in the opposite direction, the contact I75 at 90 to the left and the contact III at 90 to the right of the direction of travel of the bomber I I.

In the operation of the transmitter of Fig. 2 a radio frequency is generated which is modulated by the A, B, C and D control frequencies when the keys 30, 3|, 32 and 33 are depressed. In this way When any one of the keys 3El33 is depressed a plane polarized wave is radiated from the antenna I i, this wave being modulated at a different predetermined frequency for each key.

The modulated radio wave transmitted from the antenna I4 is received by the antenna system 2223 of the bomb II shown in Fig. 3 and selectively operates the power tubes 55-68 of the receiver I59. The power tubes 85-58 will in turn energize the solenoids 'IIT4 thru the distributing system controlled by the brushes II5IIB.

If the bomb I! does not rotate about its longitudinal axis it will assume the position shown in Figs. la and 8 in which case the rudders 2| will control the direction of motion of the bomb II in the plane in which the bomber II is travelling as indicated by the arrow 225 and the rudders I9 will control the direction of motion in a plane at right angles to the direction of motion of the bomber I I. If, for example, it is desired to deflect the bomb I I in the direction in which the bomber II is travelling the key 33 of the transmitter I60 is depressed which causes the D frequency to be transmitted. The radiated wave is picked up by the receiving antenna 22--23 on the bomb I7 and actuates the power tube 68. The plate of the tube 68 is connected thru conductor I68, brush I64, slip ring I'M, brush I15, segment I82 and conductor I86 to the solenoid I4 which is thereby energized. The energization of the solenoid I4 causes the valve 93 to be moved to the left and will allow air under pressure from the tank 81 to enter the left hand end of the cylinder 85. This will cause the piston 83 to move to the right which, by means of the rod 82 and link BI will cause a rotation of the rudders 2| in a counter-clockwise direction as seen in Fig. 4. As seen in Fig. 8 the rudders will move in the direction of the arrows 225. This will cause the bomb I! to be deflected in the direction in which the bomber I I is travelling.

If it is desired to deflect the bomb I1 in the opposite direction the key 32 is depressed causing the transmission of the C frequency which energizes power tube 67. As this tube is connected thru the distributing system to the solenoid I3 this solenoid will be energized causing the rudders 2! to be rotated in a clockwise direction as seen in Fig. 4 to deflect the bomb IT to the rear. As seen in Fig. 8 the rudders will move in the direction of the arrows 221. In a similar manner the transmission of the A frequency will cause the nergization of solenoid II to operate the rudders I9 to deflect the bomb to the left and the transmission of the B frequency will deflect the bomb to the right, as seen in Fig. 8.

If during its descent the bomb I1 should rotate about its longitudinal axis, for example, 90 degrees into the position shown in Fig. 9 the rudders I9 will then control the deflection of the bomb in the direction of the arrow 225 and the rudders 2| will control its deflection at right angles thereto. The gyroscope I94 however, together with the brushes I I5-I I8 will remain fixed in space. Due to the rotation of the bomb II thru degrees the segments I8II84 will be rotated into the position shown in Fig. 10.

If it is desired to deflect the bomb IT in the direction of the arrow 225, the key 33 of the transmitter I68 is depressed causing the D frequency to be transmitted. This as already described actuates the power tube 68. The plate of this tube is now connected thru conductor I68, brush I64, slip ring I14, brush I15, segment NH and conductor I35 to the solenoid II, as shown in Fig. 10, thus energizing solenoid 'II. The energization of solenoid II causes the valve 92 to be moved to the right as seen in Fig. 4 thus allowing air to enter the right hand side of the cylinder 84. This will cause the piston 83 to move to the left which, by means of the rod 82 and link 8| will cause the rudders I9 to move in the direction of the arrows 228 as shown in Fig. 9. This will caus the bomb II to be deflected in the direction of the arrow 225 as desired.

It is thus seen that by depressing the key 33 the bomb II will always be deflected in the direction of the arrow 225, that is in the direction in which the bomber II is travelling, no matter how much the bomb Il may have rotated about its longitudinal axis because the brush IIB will always be held flxed in space by the gyroscope I94 and will therefore engage the proper one of the segments I3II8 t so as to energize the proper solenoid EI? E to cause the bomb to be deflected in the direction of the arrow 225. In a similar manner, by depressing the key 32 the bomb I! will always be deflected in the opposite direction. By depressing the keys 30 and 3| the bomb will always be deflected to the left or right regardless of how much it may have rotated about its longitudinal axis during its descent.

Although only a few of the various forms in which this invention may be embodied have been shown herein, it is to be understood that the invention is not limited to any specific construction but may be embodied in various forms without departing from the spirit of the invention as defined by the appended claims.

What is claimed is:

1. A bomb control system comprising in combination, a carrier bourne signal transmitting apparatus including means to transmit selective control signals, and a bomb having signal receiving means responsive to said signals, rudders to control the path of descent of said bomb, rudder control mechanisms, selector mechanism mounted to turn freely in said bomb, gyrostabilized mechanism connected to stabilize said selector mechanism in azimuth regardless of the rotation of said bomb, means connecting said selector mechanism to select the rudder control mechanism which bears a predetermined azimuth position with respect thereto, and means selective- 1y responsive to said received signals to actuate the selected rudder control mechanism for deflecting said bomb in a direction determined by the control signal.

2. A bomb control system comprising in combination, a carrier bourne signal transmitting apparatus including means to transmit selective control signals, and a bomb having signal-receiving means including channels selectively responsive to said control signals, rudders to con trol the path of descent of said bomb in two directions, rudder control mechanisms therefor, selector mechanism mounted to turn freely in said bomb, gyrostabilized mechanism connected to stabilize said selector mechanism in azimuth regardless of the rotation of said bomb, means connecting said selector mechanism to select the rudder control mechanism which bears a predetermined azimuth position with respect thereto, and means selectively responsive to said received signals to actuate the selected rudder control mechanism for deflecting said bomb in a direction determined by the control signal.

8 adapted to transmit radio signals and in which the receiving means on said bomb isresponsive to said radio signals.

4. A bomb control system as set forth in claim 1 in'which said receiving means on said bomb comprises means responsive only to signals received from above whereby interference by ground signals is eliminated.

5. A bomb control system as set forth in claim 1 in which a pair of crossed rudders is rovided to control the path of descent of said bomb in two directions at right angles to each other and said gyrostabilized mechanism selects the rudder control mechanism having a position in space suited 3. A bomb control system as set forth in claim 1 15 to deflect the bomb in the desired direction.

in which the signal transmitting apparatus is JOHN HAYS HANIMOND, JR. 

